New hypervelocity capabilities for scramjet testing have recently been demonstrated in the HYPULSE Shock-Expansion Tunnel (SET). With NASA's continuing interests in scramjet testing at hypervelocity conditions (Mach 12 and above), a SET nozzle was designed and added to the HYPULSE facility. Results of tests conducted to establish SET operational conditions and facility nozzle calibration are presented and discussed for a Mach 15 (M15) flight enthalpy. The measurements and detailed computational fluid dynamics calculations (CFD) show the nozzle delivers a test gas with sufficiently wide core size to be suitable for free-jet testing of scramjet engine models of similar scale as, those tested in conventional low Mach number blow-down test facilities.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Hypervelocity Capability of the HYPULSE Shock-Expansion Tunnel for Scramjet Testing


    Contributors:
    R. O. Foelsche (author) / R. C. Rogers (author) / C. Y. Tsai (author) / R. J. Bakos (author) / A. T. Shih (author)

    Publication date :

    2001


    Size :

    10 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Hypervelocity Capability of the HYPULSE Shock-Expansion Tunnel for Scramjet Testing

    Foelsche, Robert O. / Rogers, R. Clayton / Tsai, Ching-Yi et al. | NTRS | 2001


    Mach 12 & 15 Scramjet Test Capabilities of the HYPULSE Shock-Expansion Tunnel

    Hass, N. E. / Shih, A. T. / Rogers, R. C. et al. | British Library Conference Proceedings | 2005




    Hypervelocity real gas capabilities of GASL's expansion tube (HYPULSE) facility

    TAMAGNO, JOSE / BAKOS, ROBERT / PULSONETTI, MARIA et al. | AIAA | 1990